EP2576991A1 - Turbomaschine mit einer vorrichtung zur verhinderung der drehung eines segments einer leitschaufelanordnung in einem gehäuse und drehschutzzapfen - Google Patents
Turbomaschine mit einer vorrichtung zur verhinderung der drehung eines segments einer leitschaufelanordnung in einem gehäuse und drehschutzzapfenInfo
- Publication number
- EP2576991A1 EP2576991A1 EP11728341.6A EP11728341A EP2576991A1 EP 2576991 A1 EP2576991 A1 EP 2576991A1 EP 11728341 A EP11728341 A EP 11728341A EP 2576991 A1 EP2576991 A1 EP 2576991A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- housing
- segment
- distributor
- pin
- rotation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000011144 upstream manufacturing Methods 0.000 claims description 21
- 230000001681 protective effect Effects 0.000 claims description 6
- 238000006073 displacement reaction Methods 0.000 claims description 2
- 230000000284 resting effect Effects 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 10
- 238000002485 combustion reaction Methods 0.000 description 3
- 230000036961 partial effect Effects 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000003449 preventive effect Effects 0.000 description 2
- 230000004888 barrier function Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 230000000670 limiting effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000002829 reductive effect Effects 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Definitions
- the present invention relates to the field of turbomachines and aims an annular distributor of axial turbine formed of distributor segments arranged in ring sectors.
- the invention relates more particularly to a device for wedging in rotation of these sectors inside the housing. Background of the invention
- a gas turbine engine as used in aeronautics comprises an upstream inlet through which air is sucked and then compressed while being guided through the compressor stages.
- the compressed air is introduced into a combustion chamber where the fuel with which it is mixed is also admitted and where the combustion takes place.
- the hot combustion gases are expanded in the various turbine stages, generally a high pressure stage immediately downstream of the chamber and receiving the gases at the highest temperature compatible with the holding of the materials. After this first expansion, the gases are expanded again by being guided through the so-called low pressure turbine stages.
- a turbine stage includes a distributor wheel upstream of a turbine impeller.
- An axial flow distributor wheel comprises a plurality of blades arranged radially with respect to the axis of the machine connecting a radially inner annular element and a radially outer annular element; the assembly forms an annular vein opposite the moving blades of a turbine wheel.
- the movable wheel is itself constituted by blades extending radially from the rim of a disc or a drum movable about an axis of rotation. The blades are traversed axially by the engine gases.
- the low pressure section of an engine thus generally comprises several turbine stages.
- the distributor wheels are segmented into a plurality of sectors distributed around the axis of the machine, each segment being formed of a plurality of vanes between two ring sectors.
- Each segment is mounted inside the turbine housing by the radially outer ring sector.
- the latter comprises an upstream retaining means and a downstream retaining means.
- These means are for example annular rails formed in the inner wall of the housing on which come bearing surfaces provided on the ring sectors of the distributor segments.
- the assembly is arranged to allow the relative expansion of the distributor relative to the housing which is a function of the variations in speed of the machine. Due to the axial symmetry of the distributor wheels and the tangential forces resulting from the gas flow passing through them, it is necessary to provide locking means for rotating sectors.
- Patent FR 2 743 603 in the name of SNECMA describes a method of mounting such distributor segments inside a housing.
- the distributor segments comprise a peripheral outer rib, perpendicular to the axis of the distributor, supported by faces, one radially outer, the other downstream, on corresponding faces of the inner wall of the housing. Clamps, formed by the downstream turbine ring at this level, retain the segments and hold them in place against the radial movements.
- a protrusion on the upstream face of the rib of each segment comprises a notch in which is housed an antirotation pin.
- This pin consists of a head housed in said notch and a rod slid into a radial bore of the housing wall. This pin thus prevents any rotational movement of the distributor segment around the axis of the latter.
- a sheet which is interposed between the segment and the inner wall of the housing.
- This thermal protection plate is supported upstream against a radial surface portion formed in the inner wall of the housing.
- the upstream edge of the protective sheet is bent radially inwards to form a pin which also bears on an upstream edge of the segment and participates in maintaining it against the upstream rail of the housing.
- Downstream the protection plate comprises a notch with a tongue in the bottom of the notch which rests against the anti-rotation pin of the segment. The tongue is actually wedged in a thin groove of the pawn.
- the present invention aims to remedy this problem.
- a turbomachine provided with a device for wedging in rotation a ring sector-shaped distributor segment housed inside an annular turbomachine casing with the interposition of a thermal protection plate between the inner wall of the casing and the outer wall of the segment, comprising an antirotation pin mounted both in a notch formed on the segment and a housing formed on the housing, the thermal protection plate comprising a tongue bearing against the antirotation counter.
- the turbomachine is characterized in that the device comprises the arrangement of a surface portion radially between the tongue and said inner wall of the housing, forming a stop in a possible radial displacement of the thermal protection plate during the operation of the turbine engine.
- the pin comprising a head housed in the notch of the segment and a rod coming into the housing formed on the housing, said surface portion is integral with the head of the antirotation pin.
- This embodiment has the advantage of only involving the antirotation pin, the rest of the parts: distributor segment, thermal protection plate and housing remaining unchanged. This results in a significant economic advantage, the existing pawn being able to be replaced by the modified pawn without modifying the surrounding pieces.
- This replacement can be carried out in nine as a preventive measure or during a repair.
- said surface portion is constituted by a shoulder machined in the head of the anti-rotation pin; more particularly said portion of surface is formed by a lug extending parallel to the axis of the distributor and bearing against the inner wall of the housing.
- the device of the invention finds an interesting application in the configuration described in patent FR 2 743 603, the distributor segment comprising a rib, perpendicular to the axis of the distributor, bearing against the inner wall of the housing and whose said notch is formed in a projection provided on one side of the rib.
- the thermal protection plate is preferably in the form of a ring sector with a notch corresponding to said projection, the tongue being formed in the bottom of the notch. More particularly, the protective plate is disposed upstream with respect to the rib of the distributor segment and the antirotation pin.
- the invention also relates to an antirotation pin suitable for use in the above device, the pin comprising a straight rod and a head with a first parallel face. to the axis of the rod and a surface portion perpendicular to said first face, on the opposite side to the rod.
- the pin comprises a tab perpendicular to the axis of the right rod, said surface portion being formed on the tab.
- the invention also relates to a gas turbine engine comprising a turbine stage with a device as described above.
- FIG. 1 represents an example of a gas turbine engine to which the invention applies
- FIG. 2 shows in axial section a partial view of a turbine distributor mounted in the casing of a gas turbine engine according to the prior art
- Figure 3 is a view in the direction of the motor axis of the distributor of Figure 2 with a torn portion;
- Figure 4 shows the anti-rotation counter of the prior art
- Figure 5 is an axial sectional view corresponding to that of Figure 2 with the modification of the invention
- Figure 6 shows the antirotation counter of the invention. Description of an embodiment
- a gas turbine engine 1 of the turbofan type comprises from upstream to downstream, here from left to right, a fan 2 with a low pressure compressor 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6 and a low turbine pressure 7.
- the low-pressure turbine 7 comprising several stages moving on the same rotor drives via a central shaft, the assembly formed by the fan 2 and the low-pressure compressor 3.
- the high-pressure turbine 6 to a single stage independently drives the high pressure compressor 4.
- FIG. 2 there is shown a partial view of the low pressure turbine section 7 at its outer circumference.
- a distributor 8 or stator is upstream of a wheel with moving blades 9 inside the casing 10 of the turbine.
- the moving wheel rotates about the axis of the machine inside a turbine ring 9 '.
- the distributor 8 is formed of vanes arranged in a wheel divided into a plurality of segments 80 distributed circumferentially around the axis of the machine. Each segment 80 comprises several adjacent fixed vanes integral with a ring sector element 81.
- the distributor segment 80 is held upstream by a rail-shaped rib 101 extending axially from the inner wall of the housing 10; an upstream hook 82 secured to the ring-sector element 81 bears against the radially outer face of the rail 101.
- the element 81 Downstream the element 81 comprises a peripheral radial rib 83, perpendicular to the axis of the distributor, which is supported by a radially outer face 83a and a downstream face 83b on corresponding faces of an annular rail 102 which extends axially from the inner wall of the housing 10 with a downstream edge turned towards the axis.
- an antirotation pin 20 is housed in a radial bore of the housing 10.
- the pin 20 is projecting inside the housing and is housed in a notch 83c machined in the rib 83 of the segment 80.
- the rib forms at this level an overthickness 83 'in which the notch is machined.
- rib 83 forms a barrier to gases upstream; there is no communication between the area upstream of the rib 83 and the downstream zone.
- the pin is fit tight in the housing bore but also in the notch 83c. It comprises two flanks 22a and 22b which are slid between the flanks of the notch machined parallel to the axis of the distributor.
- the notch is open upstream and is located at the center of the segment. In this way the segment 80 is held fixed in rotation relative to the housing while being able to expand circumferentially on either side of the pin and move axially to a certain extent.
- a thermal protection plate 30 is disposed between the ring sector 81 of the segment 80 and the inner wall of the housing.
- the sheet has a generally ring-shaped shape which upstream rests against a stop surface formed in the housing which may be at the level of the upstream rail 101. Downstream the protective plate 30 is cut into a notch along the contour of the projection 83 'of the rib. A tongue 30a in the bottom of the notch bears against the anti-rotation pin 20.
- the sheet being slightly deformable a spring effect may be provided to ensure the maintenance of the sheet during operation of the turbomachine.
- Figure 4 shows the anti-rotation counter of the prior art alone. It comprises a cylindrical rod 21 whose diameter allows a tight fit in the bore of the housing.
- the pin comprises a head 22 forming the bar of a T with the rod 21. This head is of parallelepipedal shape with two flanks 22a and 22b parallel to the axis of the rod 21 and between them.
- the tongue 30a of the protective plate bears against the face perpendicular to the first two 22a and 22b, disposed upstream when the pin is in the notch 83c of the rib 83.
- the antirotation counter has been modified.
- the antirotation peg according to the invention bears the same references as the prior art pin to which 100 has been added.
- This pin 120 is visible in Figures 5 and 6. It is similar to the pin 20 with a rod 121 a head 122 and flanks 122a and 122b. The dimensions are the same than that of the pin 20. It further comprises a tab 122c which extends perpendicular to the axis of the rod 121 and the width of the head 120. It is disposed between the rod and the head. Its thickness is calibrated. Figure 5 shows the new pin 120 in position. As the pin 20 it ensures the rotation of the distributor relative to the housing 10. It should be noted that compared to the prior art only the pin has been modified. The other elements: distributor, sheet and housing are the same. The tongue is in abutment against the upstream side of the head 122 of the antirotation pin.
- the tab 122c resting against the housing forms a surface against which the downstream edge of the sheet is likely to abut. If a friction occurs during the operation of the turbomachine, the area impaired by wear will be the surface of the tab 122c turned inward; in repair, it will suffice if necessary to replace the pin 120 without having to reload the inner wall of the housing. The cost of repair will be greatly reduced.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1054263A FR2960591B1 (fr) | 2010-06-01 | 2010-06-01 | Dispositif pour caler en rotation un segment de distributeur dans un carter de turbomachine ; pion antirotation |
PCT/FR2011/051251 WO2011151596A1 (fr) | 2010-06-01 | 2011-05-31 | Turbomachine avec un dispositif pour caler en rotation un segment de distributeur dans un carter; pion antirotation |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2576991A1 true EP2576991A1 (de) | 2013-04-10 |
EP2576991B1 EP2576991B1 (de) | 2017-01-25 |
Family
ID=43447918
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11728341.6A Active EP2576991B1 (de) | 2010-06-01 | 2011-05-31 | Turbomaschine mit einer vorrichtung zur verhinderung der drehung eines segments einer leitschaufelanordnung in einem gehäuse |
Country Status (9)
Country | Link |
---|---|
US (1) | US9562441B2 (de) |
EP (1) | EP2576991B1 (de) |
JP (1) | JP5796066B2 (de) |
CN (1) | CN102918230B (de) |
BR (1) | BR112012029475A2 (de) |
CA (1) | CA2800262A1 (de) |
FR (1) | FR2960591B1 (de) |
RU (1) | RU2558174C2 (de) |
WO (1) | WO2011151596A1 (de) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2985792B1 (fr) | 2012-01-18 | 2014-02-07 | Snecma | Secteur angulaire de redresseur a amortissement de vibrations par coin pour compresseur de turbomachine |
US9051849B2 (en) * | 2012-02-13 | 2015-06-09 | United Technologies Corporation | Anti-rotation stator segments |
FR2989724B1 (fr) * | 2012-04-20 | 2015-12-25 | Snecma | Etage de turbine pour une turbomachine |
US10240467B2 (en) | 2012-08-03 | 2019-03-26 | United Technologies Corporation | Anti-rotation lug for a gas turbine engine stator assembly |
FR2995340A1 (fr) * | 2012-09-12 | 2014-03-14 | Snecma | Tole de protection thermique avec butee radiale, notamment pour distributeur de turbomachine |
FR3002272A1 (fr) * | 2013-02-19 | 2014-08-22 | Snecma | Secteur de distributeur a anti-rotation pour secteur adjacent |
FR3003894B1 (fr) * | 2013-03-29 | 2017-10-27 | Snecma | Organe de verrouillage en rotation pour un distributeur et un anneau d'une turbomachine |
FR3039201B1 (fr) * | 2015-07-22 | 2017-07-21 | Snecma | Partie de turbomachine a tole de protection thermique pourvue d'epingles |
US10280773B2 (en) | 2016-04-06 | 2019-05-07 | General Electric Company | Turbomachine alignment key and related turbomachine |
FR3069014B1 (fr) * | 2017-07-11 | 2021-02-26 | Safran Aircraft Engines | Partie de turbomachine a tole ressort |
FR3085412B1 (fr) * | 2018-08-31 | 2020-12-04 | Safran Aircraft Engines | Secteur de distributeur d'une turbomachine comprenant une encoche anti-rotation a insert d'usure |
FR3096397B1 (fr) | 2019-05-21 | 2021-04-16 | Safran Aircraft Engines | Pion amovible sur distributeur de turbomachine |
GB2588929B (en) * | 2019-11-14 | 2023-09-27 | Cummins Ltd | Pin member for turbine |
CN117569923B (zh) * | 2024-01-12 | 2024-04-05 | 成都中科翼能科技有限公司 | 一种燃气轮机涡轮支点结构 |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3841787A (en) * | 1973-09-05 | 1974-10-15 | Westinghouse Electric Corp | Axial flow turbine structure |
US4650394A (en) * | 1984-11-13 | 1987-03-17 | United Technologies Corporation | Coolable seal assembly for a gas turbine engine |
FR2635562B1 (fr) * | 1988-08-18 | 1993-12-24 | Snecma | Anneau de stator de turbine associe a un support de liaison au carter de turbine |
GB2239678B (en) * | 1989-12-08 | 1993-03-03 | Rolls Royce Plc | Gas turbine engine blade shroud assembly |
US5201846A (en) * | 1991-11-29 | 1993-04-13 | General Electric Company | Low-pressure turbine heat shield |
FR2743603B1 (fr) * | 1996-01-11 | 1998-02-13 | Snecma | Dispositif de jonction de segments d'un distributeur circulaire a un carter de turbomachine |
DE19959665A1 (de) * | 1999-12-10 | 2001-06-13 | Rolls Royce Deutschland | Befestigungsanordnung für die den Strömungskanal einer Strömungsmaschine begrenzenden Wandsegmente |
DE10048156A1 (de) * | 2000-09-28 | 2002-04-11 | Rolls Royce Deutschland | Turbinendeckbandsegmentbefestigung |
FR2829525B1 (fr) * | 2001-09-13 | 2004-03-12 | Snecma Moteurs | Assemblage de secteurs d'un distributeur de turbine a un carter |
DE10312956B4 (de) * | 2003-03-22 | 2011-08-11 | MTU Aero Engines GmbH, 80995 | Anordnung für das axiale und radiale Festlegen einer Leitschaufelbaugruppe in dem Gehäuse eines Turbinentriebwerkes |
FR2899274B1 (fr) * | 2006-03-30 | 2012-08-17 | Snecma | Dispositif de fixation de secteurs d'anneau autour d'une roue de turbine d'une turbomachine |
FR2899275A1 (fr) * | 2006-03-30 | 2007-10-05 | Snecma Sa | Dispositif de fixation de secteurs d'anneau sur un carter de turbine d'une turbomachine |
FR2941488B1 (fr) * | 2009-01-28 | 2011-09-16 | Snecma | Anneau de turbine a encoche anti-rotation |
-
2010
- 2010-06-01 FR FR1054263A patent/FR2960591B1/fr active Active
-
2011
- 2011-05-31 US US13/700,641 patent/US9562441B2/en active Active
- 2011-05-31 CA CA2800262A patent/CA2800262A1/fr not_active Abandoned
- 2011-05-31 RU RU2012152657/06A patent/RU2558174C2/ru active
- 2011-05-31 JP JP2013512980A patent/JP5796066B2/ja not_active Expired - Fee Related
- 2011-05-31 BR BR112012029475A patent/BR112012029475A2/pt not_active IP Right Cessation
- 2011-05-31 CN CN201180026649.5A patent/CN102918230B/zh active Active
- 2011-05-31 EP EP11728341.6A patent/EP2576991B1/de active Active
- 2011-05-31 WO PCT/FR2011/051251 patent/WO2011151596A1/fr active Application Filing
Non-Patent Citations (1)
Title |
---|
See references of WO2011151596A1 * |
Also Published As
Publication number | Publication date |
---|---|
BR112012029475A2 (pt) | 2017-01-24 |
FR2960591B1 (fr) | 2012-08-24 |
CA2800262A1 (fr) | 2011-12-08 |
RU2012152657A (ru) | 2014-07-20 |
JP5796066B2 (ja) | 2015-10-21 |
US9562441B2 (en) | 2017-02-07 |
CN102918230B (zh) | 2015-08-26 |
WO2011151596A1 (fr) | 2011-12-08 |
EP2576991B1 (de) | 2017-01-25 |
RU2558174C2 (ru) | 2015-07-27 |
FR2960591A1 (fr) | 2011-12-02 |
US20130078086A1 (en) | 2013-03-28 |
CN102918230A (zh) | 2013-02-06 |
JP2013531165A (ja) | 2013-08-01 |
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